CA2672457C - Dispositif de scellement de bouclier thermique, pour chambre de combustion d'un moteur a turbine - Google Patents

Dispositif de scellement de bouclier thermique, pour chambre de combustion d'un moteur a turbine Download PDF

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Publication number
CA2672457C
CA2672457C CA2672457A CA2672457A CA2672457C CA 2672457 C CA2672457 C CA 2672457C CA 2672457 A CA2672457 A CA 2672457A CA 2672457 A CA2672457 A CA 2672457A CA 2672457 C CA2672457 C CA 2672457C
Authority
CA
Canada
Prior art keywords
combustor
heat shield
shield panels
radially
rail
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
CA2672457A
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English (en)
Other versions
CA2672457A1 (fr
Inventor
Eduardo Hawie
Hayley Ozem
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Pratt and Whitney Canada Corp
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Pratt and Whitney Canada Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Publication of CA2672457A1 publication Critical patent/CA2672457A1/fr
Application granted granted Critical
Publication of CA2672457C publication Critical patent/CA2672457C/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Dispositif d'étanchéité pour chemise thermique de chambre de combustion comprenant un profilé d'étanchéité s'étendant de la coque de la chemise de la chambre de combustion à la sortie de la chambre pour entrer en prise de façon étanche avec une partie d'extrémité en aval sans profilé de la chemise thermique de la chambre de combustion. Le profilé d'étanchéité est décalé par rapport au passage d'aubes en aval. Il est ainsi possible de minimiser l'effet de cascade entre la chambre de combustion et l'aube, et donc de réduire l'effet de tourbillon en fer à cheval sur le bord d'attaque des aubes de turbine.
CA2672457A 2008-10-22 2009-07-16 Dispositif de scellement de bouclier thermique, pour chambre de combustion d'un moteur a turbine Expired - Fee Related CA2672457C (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/255,995 US8266914B2 (en) 2008-10-22 2008-10-22 Heat shield sealing for gas turbine engine combustor
US12/255,995 2008-10-22

Publications (2)

Publication Number Publication Date
CA2672457A1 CA2672457A1 (fr) 2010-04-22
CA2672457C true CA2672457C (fr) 2011-08-02

Family

ID=42107536

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2672457A Expired - Fee Related CA2672457C (fr) 2008-10-22 2009-07-16 Dispositif de scellement de bouclier thermique, pour chambre de combustion d'un moteur a turbine

Country Status (2)

Country Link
US (1) US8266914B2 (fr)
CA (1) CA2672457C (fr)

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WO2015103357A1 (fr) 2013-12-31 2015-07-09 United Technologies Corporation Ensemble paroi de moteur à turbine à gaz à architecture d'écoulement améliorée
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US10538013B2 (en) 2014-05-08 2020-01-21 United Technologies Corporation Integral ceramic matrix composite fastener with non-polymer rigidization
US10132498B2 (en) * 2015-01-20 2018-11-20 United Technologies Corporation Thermal barrier coating of a combustor dilution hole
US10267521B2 (en) * 2015-04-13 2019-04-23 Pratt & Whitney Canada Corp. Combustor heat shield
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US10386067B2 (en) * 2016-09-15 2019-08-20 United Technologies Corporation Wall panel assembly for a gas turbine engine
US10823410B2 (en) 2016-10-26 2020-11-03 Raytheon Technologies Corporation Cast combustor liner panel radius for gas turbine engine combustor
US10670269B2 (en) 2016-10-26 2020-06-02 Raytheon Technologies Corporation Cast combustor liner panel gating feature for a gas turbine engine combustor
US10669939B2 (en) 2016-10-26 2020-06-02 Raytheon Technologies Corporation Combustor seal for a gas turbine engine combustor
US10830448B2 (en) 2016-10-26 2020-11-10 Raytheon Technologies Corporation Combustor liner panel with a multiple of heat transfer augmentors for a gas turbine engine combustor
US10935243B2 (en) 2016-11-30 2021-03-02 Raytheon Technologies Corporation Regulated combustor liner panel for a gas turbine engine combustor
US10739001B2 (en) 2017-02-14 2020-08-11 Raytheon Technologies Corporation Combustor liner panel shell interface for a gas turbine engine combustor
US10830434B2 (en) 2017-02-23 2020-11-10 Raytheon Technologies Corporation Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor
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US10718521B2 (en) 2017-02-23 2020-07-21 Raytheon Technologies Corporation Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor
US10941937B2 (en) 2017-03-20 2021-03-09 Raytheon Technologies Corporation Combustor liner with gasket for gas turbine engine
EP3412871B1 (fr) 2017-06-09 2021-04-28 Ge Avio S.r.l. Joint pour aube directrice de turbine à gaz
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Also Published As

Publication number Publication date
US20100095678A1 (en) 2010-04-22
US8266914B2 (en) 2012-09-18
CA2672457A1 (fr) 2010-04-22

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